Container structure for separate storage of liquid rocket propellants



Sept. 8, 1959 J. D. McKn-:RNAN 2,902,822

CONTAINER STRUCTURE FOR SEPARATE STORAGE OF LIQUID ROCKET PROPELLANTSFiled Feb. 2s. 1954 1N VENTOR ATTORNEYS Fla. 4

FIG. l

'lll/l assignments, to the United States of America as represented bythe Secretary of the Navy Application February 23, 1954, Serial No.412,127

2 Claims. (Cl. 6I)-'3`S.6)

The present invention `relates to a liquid propellant container andsupply system for bi-propellant rockets which facilitates separatestorage of each of the propellants.

The liquid propellant systems heretofore known have utilized xedcontainers and have generally relied upon compressed gas or mechanicalpumps to introduce the propellants into the injector. The use ofcompressed gas necessitates a storage chamber for the gas, thus addingto the weight land space requirements of the system, while mechanicalpumps and the turbines employed to operate Vthem are expensive,complicated and subject to frequent failure. In addition, the use offixed propellant containers in close proximity to each other has createda safety hazard in shipboard handling and storage due to the likelihoodof rupture of the containers as a result of rough seas, with consequentmingling of the propellants.

In the present invention separable propellant capsules are used inconjunction with a gas pressure producing means to introduce thepropellants directly into the injector without the use of mechanicalpumps or compressed gas pressure systems.

An object of the present invention is the provision of an inexpensiveand simple container and supply system for liquid rocket propellants.

Another object is the provision of a container and supply system forliquid propellants which allows separate storage of each propellant.

A further object of the invention is the provision of a container andsupply system for liquid rocket propellants which facilitates deliveryof the propellants to the injector without the use of pumps, compressedgas` systems or any connecting piping.

Other objects and many of the attendant advantages of this inventionwill be readily appreciated as the same becomes better understood byreference to the following detailed description when considered inconnection with the accompanying drawings wherein:

Fig. 1 is a side elevation view in section of a rocket embodying thepresent invention.

Figs. 2 and 3 are elevation views in section showing the propellantcapsules of Fig. l separated for individual storage.

Fig. 4. is a sectional view of another embodiment of a tubular capsulesimilar to that of Fig. 2.

Fig. 5 is a sectional view of another embodiment of a cylindricalcapsule similar to that of Fig. 3.

Referring more particularly to the drawings, the rocket 10, Fig. 1,contains two propellant capsules 11 and 17 nested in concentricrelation, both of said capsules being formed of a light strong materialsuch as plastic, aluminum or the like. The capsule 11 is of elongatedannular construction having ends 12 and 15, an exterior wall 13 and aninterior wall 14 spaced inwardly therefrom, said interior wall dening acentral bore 16 extending throughout the longitudinal axis of thecapsule. The remaining capsule 17 is of cylindrical construction havingends Rrice 18 and 19 and an exterior wall 21; Both ends of each of thecapsules are formed of a yieldable material which, being frangible, willrupture under the application of pressure.

The rocket 10, as illustrated in Fig. l, is in condition for firing;however, for purposes of shipboard handling and storage the rocket isseparated into the two components illustrated in Fig. 2 and Fig. 3. Eachof these components may be stored in a separate compartment and the twobrought together just prior to firing of the rocket. In the component ofFig. Z the capsule 11 is retained within the rocket casing 22 by meansof the end plug 23 which has external threads 24 engaged with theinternally threaded portion 25 at the rearward end of the rocket casing.A partition 26 is positioned at the forward end of the casing and ispierced by a plurality of gas ports 27 distributed about the areathereof. On the rearward side of the partition 26 adjacent to the end 15of-capsule 11, the gas ports 27 are each covered by a burst disc 28. Onthe same side of the partition 26 is a rearwardly opening circulargroove 29 with a packing 31 located at the bottom thereof. On theforward side of the partition a gas producing agent 32 is mounted inclose proximity to the igniter 33.

In the component of Fig. 3 the propellant capsule 17 is received withinthe tubular member 34 which is welded to the injector 35 as at 36, thecapsule being retained in the tubular member by temporary closure 37fitted in the open end of the member 34. The injector 35 is pierced by aplurality of ports 38 which are closed by the burst discs 39, and aboutthe periphery of the injector is a groove 41 to receive `the O-ring seal42. The O-ring 42, the nozzle section 43 and the externally threaded nut44 are all separable from the injector assembly and can be stored andhandled either with the injector assembly or separate therefrom asdesired.

VIn the operation of the rocket 10, the component of Fig. 3 is firstassembled with the component of Fig. 2, this is accomplished by removingthe temporary closure 37 and the end plug 23, tting the O-ring 42 in thegroove 41 and inserting the tubular member 34 in the bore 16 such thatthe open end thereof seats in groove 29 and is sealed by packing 31,then inserting the forward end of the nozzle section 43 in the open endof the rocket casing adjacent to the injector 3S and screwing the nut 44into place in engagement with the threaded portion 25 to hold the entireassembly in place. The rocket is then ready to lbe red. To lire therocket, the igniter 33 is activated by connection with a source ofelectrical current (not shown) and the gas producing agent is ignited.As the gas producing agent burns, it produces a gas which builds uppressure forward of the partition 26. When suicient pressure is builtup, the burst discs 28 are ruptured and the gas ows through the ports 27into contact with the yieldable ends 15 and 19 of the capsules 11 and17. The pressure of the gas ruptures ends 15 and 19 `directly and istransmitted through the propellants to rupture ends 12 and 18, thepropellants are then forced yfrom the capsules into Contact with theburst discs 39. Pressure is then built up on the propellants until theburst discs 39 are ruptured, the propellants are then forced through theports 38 where they are intermingled and injected into the nozzlesection 43 where they are burned to create the thrust for propulsion ofthe rocket. The gas producing agent 32 continues to burn and produce gasuntil all of the propellants have been forced from the capsules andinjected into the nozzle section. If required, an igniter may beprovided in the nozzle section to ignite the propellants orself-igniting propellants may -be utilized.

In the alternative embodiments of the annular capr 3 sule and thecylindrical capsule shown in Figs. 4 and 5 respectively, the interiorwall 46 and rearward end 47 of the capsule 45 are formed of a light,relatively stitr` material, such as plastic or the like, and theexterior wall 48 and the forward end 49 are formed of a thin, yieldable,pliable membrane, the end 47 having a plurality of frangible inserts 51spaced about its area. YIn Capsule 52, the rear end 53 and rear portion54 of 'wall 55 are formed of a light, relatively stii material, suchv asplastic or the like, and the forward end 56 and the forward portion 57of wall 55 are formed of a thin, yieldable, pliable membrane, the end 53having a frang'ible insert 58 located therein. A rocket equipped withthe capsules 45 and 52 operates in a similar manner to that of` therocket of Fig. 1, except that the gas pressure on the yieldable ends 49and 56 is transmitted through the propellants to rupture inserts 51 and58. The pliable yieldable, portions of the capsules are thenprogressively collapsed to the dotted line positions shown in Figs. 4and 5 forcing the propellants out of the capsules into the injector.This operation is advantageous in that the pressurizing gas is separatedfrom the propellants during their expulsion from the capsules.

The present invention is especially useful in bi-propellant rocketssince it permits of separate storage and handling of the propellants,but the disclosed system can be used equally as well in amono-propellant rocket, in which case both capsules would contain thesame propellant and separate storage would be unnecessary.

Obviously many modifications and variations of the Y present inventionare possible in the light of the above teachings. It is therefore to beunderstood that within the scope of the appended claims the inventionmaybe practiced otherwise than as specifically described.

What is claimed is:

1. A bi-propellant rocket assembly having a casing, a gas producingmeans and igniter in one end of said casing, a partition having gasports covered by burst discs positioned adjacent said gas producingmeans, an injector having gas ports covered by burst discs in the otherend of said casing, said injector, partition and casing forming apropellant storagespace, a tubular member concentric with the casing andextending the length of said storage space, the casing and tubularmember forming a rst storage chamber and the interior of said tubularmember forming a second storage chamber, said injector and casing havingcooperating securing means whereby ready access may ybe had to saidfirst and second storage chambers by disengaging the injector from thecasing, and first and second removable propellant container means insaid rst and second storage chambers, respectively, for separatelystoring two dilerent propellants, said rst container means comprising anelongated annular capsule, and said second container means comprising acylindrical capsule having closed ends, the ends of each capsule beingyieldable and positioned adjacent a gas` port in said partition andinjector.

2. A bi-propellant rocket assembly having a casing, a gas producingmeans and igniter in one end of said casing, a partition having gasports covered by burst discs positioned adjacent said gas producingmeans, an injector having gas ports covered by burst discs positioned inthe other end of said casing, said injector, partition and casingforming a propellant storage chamber, and removable propellant containermeans positioned in said chamber for separately storing two differentpropellants, said container means compris-ing first and second capsulesof equal length extending the length of said chamber, said rst capsulebeing of elongated annular form having an inner wall of relatively stiifmaterial and a spaced outer wall of yieldable material, and said secondcapsule being cylindrical in form and nested concentrically within saidrst capsule, the forward portion of the second capsule adjacent saidpartition being formed of a yieldable mastii material havingA an orificecovered by a frangible disc in the end adjacent said injector.

References Cited in the tile of this patent UNITED STATES PATENTS

